Flow control in pulse detonation engines is accomplished using magnetohydrodynamic principles. The pulse detonation engine includes a tube having an open forward end and an open aft end and a fuel-air inlet formed in the tube at the forward end. An igniter is disposed in the tube at a location intermediate the forward end and the aft end. A magnetohydrodynamic flow control system is located between the igniter and the fuel-air inlet for controlling detonation in the tube forward of the igniter. The magnetohydrodynamic flow control system utilizes magnetic and electric fields forward of the igniter to dissipate or at least reduce the ignition potential of the forward traveling detonation flame front.
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1. In a pulse detonation engine comprising a tube having a forward end and an aft end and an igniter disposed in said tube at a location intermediate said forward end and said aft end, a method for controlling detonation in said tube forward of said igniter, said method comprising:
filling said tube with a fuel-air mixture; detonating said fuel-air mixture so as to generate a forward detonation wave group comprising a forward pressure wave and a forward flame front and an aft detonation wave group comprising an aft pressure wave and an aft flame front; and creating a magnetic field forward of said igniter to dissipate said forward flame front.
2. The method of
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This application is a division of application Ser. No. 09/756,895, filed Jan. 9, 2001 (U.S. Pat. No. 6,484,492).
This invention relates generally to pulse detonation engines and more particularly to pulse detonation engines utilizing magnetohydrodynamic flow control.
Most internal combustion engines currently used for propulsion rely on deflagration combustion whereby the combustion effects occur at relatively slow rates (i.e., less than the speed of sound within the combustible mixture) and at constant pressure. Detonation combustion, however, occurs at rates well in excess of the speed of sound and simultaneously provides a significant pressure rise. Because of the advantageous thermodynamic cycle, there is a high degree of interest in developing propulsive devices that rely on detonation combustion rather than deflagration combustion.
One such device is a pulse detonation engine that uses an intermittent combustion process to create a temperature and pressure rise by detonating a flammable mixture. The conditions for detonation are governed by the environment of the mixture (pressure, temperature, equivalence ratio, etc.) such that when enough energy is released to start ignition, the chemical kinetics occur at supersonic speeds. A pulse detonation engine is typically a tube of a specified length that is open at the aft end and includes some sort of valve device at the front end to keep the detonation process from traveling forward. In operation, a charge of air and fuel is fed into the tube through the valve, and the valve is then closed. Detonation of the fuel-air mixture is initiated by an igniter located in the tube, and the resulting detonation shock waves travel down the tube, raising both the temperature and the pressure of the products. The combustion products are expelled out of the open aft end, creating a pulse of forward thrust. When the shock waves have reflected within the tube to the appropriate conditions, a new charge is fed into the tube through the valve and the cycle repeats. It is generally desirable to generate pulses at a high frequency to produce smooth, nearly steady state propulsion.
Upon ignition, the resulting pressure waves and detonation flame front will tend to travel in both longitudinal directions. In current pulse detonation devices, however, ignition is initiated at the forward end of the tube so that the waves will generally travel downstream toward the open exhaust end. The valve is provided at the forward end of the tube to prevent pressure waves from escaping out the front of the device and, more importantly, to prohibit the detonation flame front from traveling into the fuel-air inlet system. The pulse detonation cycle requires that the valve operate at extremely high temperatures and pressures and must also operate at exceedingly high frequencies to produce smooth propulsion. These conditions significantly reduce the high cycle fatigue (HCF) reliability of conventional valve systems, such as poppet or flapper-type valves.
Accordingly, it would be desirable to have a high frequency valving or flow control system for pulse detonation engines that is lightweight, reliable, easily controlled and offers minimal performance loss.
The above-mentioned need is met by the present invention, which provides a pulse detonation engine that includes a tube having an open forward end and an open aft end and a fuel-air inlet formed in the tube at the forward end. An igniter is disposed in the tube at a location intermediate the forward end and the aft end. A magnetohydrodynamic flow control system is located between the igniter and the fuel-air inlet for controlling detonation in the tube forward of the igniter. The magnetohydrodynamic flow control system creates a magnetic field forward of the igniter to dissipate the forward traveling detonation flame front.
The present invention and its advantages over the prior art will become apparent upon reading the following detailed description and the appended claims with reference to the accompanying drawings.
The subject matter that is regarded as the invention is particularly pointed out and distinctly claimed in the concluding part of the specification. The invention, however, may be best understood by reference to the following description taken in conjunction with the accompanying drawing figures in which:
Referring to the drawings wherein identical reference numerals denote the same elements throughout the various views,
An igniter 24 is provided in the tube 12 at a location intermediate the forward and aft ends 16, 18, and preferably closer to the forward end 16 than the aft end 18. The igniter 24 produces sufficient energy to detonate the fuel-air mixture in the combustion chamber 14. The region of the combustion chamber 14 in the immediate vicinity of the igniter 24 is referred to herein as the detonation zone. Detonation combustion depends on the pressure, temperature and equivalence ratio of the fuel-air mixture, as well as the amount of energy released to start ignition. By locating the detonation zone closer to the forward end 16, a larger portion of the tube length is devoted to generating thrust. The overall length of the tube 12 will depend on the desired operating frequency of the pulse detonation engine 10.
A magnetohydrodynamic (MHD) flow control system 26 is located between the detonation zone and the fuel-air inlet 20 for controlling the detonation process in the forward portion of the tube 12. The MHD flow control system 26 comprises an electric field coil 28 wrapped around the exterior of the tube 12 at an axial location that is between the igniter 24 and the fuel-air inlet 20. A pair of magnets 30 are arranged in proximity to the electric field coil 28 and on opposite sides of the tube 12 so that a magnetic field is created in the tube 12 in a direction perpendicular to the longitudinal axis of the tube 12, as indicated by the arrows B. The magnets can be either permanent magnets or electromagnets. However, the use of permanent magnets would result in a passive system not requiring an additional energy input.
Upon detonation of the fuel-air mixture in the combustion chamber 14, detonation wave groups (pressure wave and flame front) will propagate in both the forward and aft directions. As depicted in
The electrical power generated by the electric field coil 28 can be used to charge the igniter 24. In this case, the electric field coil 28 is connected to a power conditioning control system 40 that is provided for directing the electrical power at the appropriate times to the igniter 24. In addition, the electricity could be used for other purposes, such as powering onboard devices in a vehicle being propelled by the pulse detonation engine 10.
The MHD flow control system 26 includes a supplemental ionization source 42 for boosting and/or maintaining the ionization of the post combustion products passing through the magnetic field. While the combustion process produces ionized combustion products, the charged particles tend to recombine quickly such that the combustion products lose their ionization. The ionization source 42 is thus provided to boost ionization and maintain the electron density of the combustion products passing through the magnetic field. Typically, an electron density of 1013 electrons per cubic centimeter is desired to achieve sufficient influence from the magnetic field. The ionization source 42 can be any device capable of supplementing ionization, such as an electron gun that bombards the combustion products with extra electrons or an RF generator that further heats the combustion products, thereby inhibiting recombination of charged particles. The ionization source 42 is preferably located at the aft end of the electric field coil 28, although it could also be located along the length of the coil 28. In addition, the inlet flow of the fuel-air mixture could be seeded with a catalyst to enhance ionization of the combustion products. Examples of suitable catalysts include potassium carbonate (powder) and cesium hydroxide (spray).
Operation of the pulse detonation engine 10 begins by filling the combustion chamber 14 with a charge of the fuel-air mixture introduced through the inlet 20. The igniter 24 is then activated to detonate the fuel-air mixture and generate the forward and aft detonation wave groups as shown in FIG. 1. The forward wave group 32, 34 travels forward in the tube 12 and is dissipated by the MHD flow control system 26 in the manner described above. The aft wave group 36, 38 travels downstream from the detonation zone through the generally longer aft portion of the tube 12, as shown in
Referring now to
An igniter 24 is provided in the tube 12 at a location intermediate the forward and aft ends 16, 18, and preferably closer to the forward end 16 than the aft end 18. The igniter 24 produces sufficient energy to detonate the fuel-air mixture in the combustion chamber 14. The region of the combustion chamber 14 in the immediate vicinity of the igniter 24 is referred to herein as the detonation zone. Detonation combustion depends on the pressure, temperature and equivalence ratio of the fuel-air mixture, as well as the amount of energy released to start ignition. By locating the detonation zone closer to the forward end 16, a larger portion of the tube length is devoted to generating thrust. The overall length of the tube 12 will depend on the desired operating frequency of the pulse detonation engine 44.
An MHD flow control system 48 is located between the detonation zone and the fuel-air inlet 20 for controlling the detonation process in the forward portion of the tube 12. The MHD flow control system 48 comprises a magnetic field coil or coils 50 connected to a real time controller 52 capable of engaging an energy source (not shown) such that an electric current flows through the coil 50. The controller 52 also controls the igniter 24 and the ionization sources 46. The magnetic field coil 50 is wrapped around the exterior of the tube 12 at an axial location that is between the igniter 24 and the fuel-air inlet 20. Thus, when the controller 52 causes an electric current to flow though the coil 50, a magnetic field is created in the portion of the tube 12 enclosed by the coil 50. Due to the ionization of the fuel in the fuel-air mixture, the charged fuel particles would be directionally influenced by the magnetic field coil 50 when it becomes energized. Thus, activation of the magnetic field coil 50 would tend to separate the fuel-air mixture in the portion of the combustor chamber 14 encircled by the coil 50. As shown in
Operation of the pulse detonation engine 44 begins by filling the combustion chamber 14 with a charge of the fuel-air mixture introduced through the inlet 20. As mentioned above, the ionization sources 46 ionize the fuel-air mixture as it enters the combustion chamber 14. The magnetic field coil 50 is not activated while the combustion chamber 14 is being filled to ensure that the fuel-air mixture remains properly mixed throughout the combustion chamber 14. The controller 52 then activates the igniter 24 to detonate the fuel-air mixture. At the same time, the controller 52 also activates the magnetic field coil 50 causing the fuel-air mixture in the region of the combustion chamber 14 that is encircled by the coil 50 to become separated. Upon detonation of the fuel-air mixture, as shown in
Meanwhile, the aft wave group 36, 38 travels downstream from the detonation zone through the generally longer aft portion of the tube 12, consuming the fuel-air mixture along the way. As the aft pressure wave 36, which is a compression wave, accelerates through the combustion chamber 14, it raises both temperature and pressure. When the aft wave group 36, 38 reaches the aft end 18 of the tube 12, the hot, high pressure combustion products are expelled out of the open aft end, creating a pulse of forward thrust. The aft pressure wave 36 is reflected at the aft end 18 as an expansion wave that propagates forward back through the tube 12. The expansion wave lowers pressure in the combustion chamber 14 so that a fresh charge of fuel-air mixture from the inlet 20 is drawn into the combustion chamber 14, thereby readying the pulse detonation engine 44 for the next cycle. The controller 52 is set up to fire the igniter 24 and activate the magnetic field coil 50 at the desired frequency, which is coordinated with the timing of the pressure wave reflections.
Turning to
An igniter 24 is provided in the tube 12 at a location intermediate the forward and aft ends 16, 18, and preferably closer to the forward end 16 than the aft end 18. The igniter 24 produces sufficient energy to detonate the fuel-air mixture in the combustion chamber 14. The region of the combustion chamber 14 in the immediate vicinity of the igniter 24 is referred to herein as the detonation zone. Detonation combustion depends on the pressure, temperature and equivalence ratio of the fuel-air mixture, as well as the amount of energy released to start ignition. By locating the detonation zone closer to the forward end 16, a larger portion of the tube length is devoted to generating thrust. The overall length of the tube 12 will depend on the desired operating frequency of the pulse detonation engine 54.
An MHD flow control system 56 is located between the detonation zone and the fuel-air inlet 20 for controlling the detonation process in the forward portion of the tube 12. The MHD flow control system 56 comprises a passive electric field coil 28 wrapped around the exterior of the tube 12 at an axial location that is between the igniter 24 and the fuel-air inlet 20. A pair of electrodes disposed on opposite sides of the tube 12 could be used as an alternative to the coil 28, as discussed above in connection with FIG. 3. An active magnetic field coil 50 is also wrapped around the exterior of the tube 12 at an axial location just forward of the electric field coil 28 and aft of the fuel-air inlet 20. A pair of magnets 30 are arranged in proximity to the electric field coil 28 and on opposite sides of the tube 12 so that a magnetic field is created in the tube 12 in a direction perpendicular to the longitudinal axis of the tube 12, as indicated by the arrows B. The magnets can be either permanent magnets or electromagnets.
The MHD flow control system 56 includes a supplemental ionization source 42 for boosting and/or maintaining the ionization of the post combustion products passing through the magnetic field. While the combustion process produces ionized combustion products, the charged particles tend to recombine quickly such that the combustion products lose their ionization. The ionization source 42 is thus provided to boost ionization and maintain the electron density of the combustion products passing through the magnetic field. The ionization source 42 is preferably located at the aft end of the electric field coil 28, although it could also be located along the length of the coil 28.
Ionized, electrically conductive material passing perpendicularly through the magnetic field created by the magnets 30 will result in an electrical current being generated in the electric field coil 28 by electromagnetic induction. As shown in
The power conditioning control system 40 also functions as a real time controller that selectively engages an energy source (not shown) such that an electric current flows through the magnetic field coil 50. When the power conditioning control system 40 causes an electric current to flow though the coil 50, a magnetic field is created in the portion of the tube 12 enclosed by the coil 50. Due to the ionization of the fuel-air mixture, the charged fuel particles would be directionally influenced by the coil 50 when it is energized. Thus, activation of the magnetic field coil 50 would tend to separate the fuel-air mixture in the portion of the combustor chamber 14 encircled by the coil 50. As shown in
Operation of the pulse detonation engine 54 begins by filling the combustion chamber 14 with a charge of the fuel-air mixture introduced through the inlet 20. As mentioned above, the ionization sources 46 ionize the fuel-air mixture as it enters the combustion chamber 14. The magnetic field coil 50 is not activated while the combustion chamber 14 is being filled to ensure that the fuel-air mixture remains properly mixed throughout the combustion chamber 14. The power conditioning control system 40 then activates the igniter 24 to detonate the fuel-air mixture. At the same time, the power conditioning control system 40 activates the magnetic field coil 50 causing the fuel-air mixture in the region of the combustion chamber 14 that is encircled by the coil 50 to become separated.
Upon detonation of the fuel-air mixture, as shown in
Meanwhile, the aft wave group 36, 38 travels downstream from the detonation zone through the generally longer aft portion of the tube 12, consuming the fuel-air mixture along the way. As the aft pressure wave 36, which is a compression wave, accelerates through the combustion chamber 14, it raises both temperature and pressure. When the aft wave group 36, 38 reaches the aft end 18 of the tube 12, the hot, high pressure combustion products are expelled out of the open aft end, creating a pulse of forward thrust. The aft pressure wave 36 is reflected at the aft end 18 as an expansion wave that propagates forward back through the tube 12. The expansion wave lowers pressure in the combustion chamber 14 so that a fresh charge of fuel-air mixture from the inlet 20 is drawn into the combustion chamber 14, thereby readying the pulse detonation engine 54 for the next cycle. The controller 52 is set up to fire the igniter 24 and activate the magnetic field coil 50 at the desired frequency, which is coordinated with the timing of the pressure wave reflections.
The foregoing has described various MHD flow control systems for pulse detonation engines. The flow control systems do not require moving parts and are thus highly reliable and capable of operating at extremely high frequencies. They are also easily controlled by electronic means. While specific embodiments of the present invention have been described, it will be apparent to those skilled in the art that various modifications thereto can be made without departing from the spirit and scope of the invention as defined in the appended claims.
Stowell, William Randolph, Meholic, Gregory Vincent
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